MEMS Mega-Pixel Micro-Thruster Array

Abstract

Public reporting burden for this collection of information is estimated to average 1 hour per response, including the ti gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comm collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Direc Davis Highway, Suite 1204, Arlington, VA 22202-4302, and small satellites flying in clusters require periodic "stationkeeping" to keep them in f lace. The required impulse is very small -the goal is not to keep the individual satellites in rigid formation, but only to keep them in well-defined orbitals with respect to one another. The necessary impulse, therefore, is only the amount needed to overcome the difference in drag between the most-affected and the least-affected satellites in the cluster. Estimates are that the differential drag can be overcome by providing -1 uNsec (micro-Newton second) to -1 mN sec (milli-Newton gecond) every 10 to 100 seconds throughout each satellite's mission. The system we are developing will do that. The thrusters have very low power and energy thresholds for ignition ( -10 mWatts, -100 Joules), and no moving parts so they are expected to be highly reliable. A single thruster array contains a quarter of a million separate thrusters. 068 SUBJECT TERMSMicro-propulsion. Micro-satellites, Nano-satellites, Pico-satellites, MEMS. Abstract. Small satellites flying in clusters require periodic "stationkeeping" to keep them in place. The required impulse is very small -the goal is not to keep the individual satellites in rigid formation, but only to keep them in well-defined Orbitals with respect to one another. The necessary impulse, therefore, is only the amount needed to overcome " e difference in drag between the most-affected and the least-affected satellites in the cluster. NUMBER OF PAGESEstimates are that the differential drag can be overcome by providing -1 |iNsec (micro-Newton second) to -1 mN sec (mi'li-Newton second) every 10 to 100 seconds throughout each satellite's mission. The system we are developing will do that. The thrusters have very low power and energy thresholds for ignition (-10 mWatts, -100 uJoules), and no moving parts so they are expected to be highly reliable. A single thruster array contains a quarter of a million separate thrusters.

Development of a low-temperature co-fired ceramic solid propellant microthruster

“…The solid propellant microthruster has many advantages over other microthrusters, such as reduced system complexity, no moving parts and very low propellant leakage possibility. Consequently, the solid propellant microthruster is being studied extensively [8][9][10][11][12]. Its main design concepts are based on the three-layer sandwich configurations, which normally comprise three parts, namely, a combustion chamber, a micronozzle (or burst diaphragm) and an igniter.…”

Development of a solid propellant microthruster with chamber and nozzle etched on a wafer surface

“…Given the above reasons, several designs for a solid propellant microthruster have been studied. These include a digital microthruster [6], a mega-pixel microthruster for small satellites [7], a microrocket for smart dust [8], a solid propellant microrocket for micropropulsion [9] and a solid propellant rocket array thruster [10]. Their main design concepts are based on three-layer sandwich configurations, which normally comprise three parts, namely, a combustion chamber, a micronozzle (or burst diaphragm) and an ignitor.…”